GB989279A - Gas turbine by-pass engine - Google Patents

Abstract

989,279. Gas turbine by-pass type jet engines. ROLLS-ROYCE Ltd. Feb. 5, 1964, No. 4988/64. Heading FlJ. [Also in Division B7] A gas turbine by-pass engine comprises a series flow arrangement of compressor, main combustion equipment, turbine, exhaust duct, and main propulsion nozzle, chßracterized in that a by-pass duct is provided which receives air from the compressor and which contains combustion equipment, there being at least one additional nozzle which is adapted for the passage therethrough of combustion gases from both the main and the by-pass combustion equipment. The embodiment described includes two additional nozzles 30 which, in conjunction with two pivotable 'eyelid' valve members 33, enable the engine to be used for vertical, transitional and horizontal flight. Additionally, the nozzle members 30 are equipped with guide vanes 32 which are rotatable to enable the thrust from the nozzles to be directed in any direction from forwards to rearwards, through vertically downwards. When the eyelids are in the position shown in full lines in Fig. 2, an after burner system 43 and 44 may be used, in conjunction with a variable area propulsion nozzle 40. The low pressure compressor 11 and the low pressure turbine 15, and the high pressure compressor 12 and the high pressure turbine 14 are coupled as pairs by concentric shafts 21, 20. The air intake for the by-pass system is between the two compressor stages, and the exhaust 26 includes area control flaps 36. A burner is provided in the by-pass section, and comprises fuel jets 25 immediately upstream of V-section annular rings 23, which stabilize the flame front. During normal forward flight, the by-pass burners are not utilized, and the flaps 36 are in a position to give minimum exit flow cross-section. A second embodiment is described which is identical, except that no afterburning or variable nozzle system is used. Specification 913,312 is referred to.